考虑约束的机载导弹导轨发射数值模拟  

Numerical simulation of missile air-launching process under rail slideway constraints

作　　者：刘刚[1] 肖中云[1] 王建涛[1] 刘钒[1] 

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,四川绵阳621000

出　　处：《空气动力学学报》2015年第2期192-197,共6页Acta Aerodynamica Sinica

摘　　要：采用计算流体动力学和刚体动力学模型耦合求解的方法,对导轨发射的机载导弹分离过程进行了模拟,导弹运动过程包含了双(多)吊挂约束、单吊挂约束和自由运动三个阶段,为了模拟单吊挂约束状态下导弹的运动,在刚体六自由度运动方程基础上,发展了约束形式的刚体动力学模型,通过计算刚体自由转动(欧拉陀螺)和旋转刚体的进动(拉格朗日陀螺)两个算例,得到与理论解吻合的计算结果,验证了运动模型的正确性。在此基础上,对某机载导弹的发射过程进行了数值模拟,模拟中根据后挂点所处不同位置分别采用直线运动、单铰链约束和六自由度运动模型。通过数值仿真,获取了发射过程的运动轨迹和姿态变化,结果表明中等攻角下翼吊导弹受到横向洗流的作用,产生较大的侧向力和偏航力矩,导致导弹发生横滚产生弹架干涉。单吊挂约束下导弹俯仰运动受到法向气动力、重力以及法向过载的作用,严苛条件下可能引起弹架干涉。Computational fluid dynamics and rigid body dynamics models are solved in a loosely coupled way to simulate a missile launched from an aircraft by rail, the motions consist of three phases, which correspond to two or multi- hanger phase, single hanger phase and free mo- tion phase. In order to simulate the motion of missiles subjected to single hanger constraint, the constrained dynamics equations are derivated from six degree of freedom motion equations, the model is verified by simulating free rotation of rigid body （Euler gyro） and procession of rotation- al rigid body（Lagrange gyro）, which shows good agreement with the theoretical solutions. After that, the launching process of a missile from an aircraft is numerically simulated, in which con- strained and non-constrained rigid-body dynamics models are switched corresponding to hanger＇s position. By numerical simulation, trajectories and attitudes profile of the missile are obtained. The results show that the missile is impacted by lateral wash flows at moderate angles of attack, resulting in large lateral force and yawing moment, causing the missile to roll rapidly and produce missile-frame interference further. In the phase of single hanger constraint, the missile tends to pitch due to normal aerodynamic force, gravity, normal overload and so on, which may lead to interference with rail launcher on harsh conditions.

关 键 词：刚体动力学 约束 陀螺 机载导弹 数值计算 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]